GAS TURBINE ENGINE WITH THIRD STREAM

Abstract

A gas turbine engine defining a centerline and a circumferential direction, the gas turbine engine including: a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the turbomachine defining a working gas flowpath and a fan duct flowpath; a primary fan driven by the turbomachine defining a primary fan tip radius R 1 and a primary fan hub radius R 2 ; a secondary fan located downstream of the primary fan and driven by the turbomachine, at least a portion of an airflow from the primary fan configured to bypass the secondary fan, the secondary fan defining a secondary fan tip radius R 3 and a secondary fan hub radius R 4 , wherein the secondary fan is configured to provide a fan duct airflow through the fan duct flowpath during operation to generate a fan duct thrust, wherein the fan duct thrust is equal to %Fn 3S of a total engine thrust during operation of the gas turbine engine at a rated speed during standard day operating conditions; wherein a ratio of R 1 to R 3 equals EFP 1 − RqR Sec . − Fan 2 1 − RqR Prim . − Fam 2 1 %Fn 3 s − 1 ; wherein EFP is between 1.5 and 11, wherein RqR Prim.-Fan is a ratio of R 1 to R 2 , and wherein RqR Sec.-Fan is a ratio of R 3 to R 4 .

Inventors

Ostdiek, David Marion

Assignees

General Electric Company

Dates

Publication Date: 20260506
Application Date: 20220901